Inlet Influence on the Pressure and Temperature Distortion Entering the Compressor of an Air Vehicle

摘要

One of the possible origins of High Cycle Fatigue in a compressor blade is the rotating stall under the influence of (rotating) inlet pressure or temperature distortion leading to a varying angle of attack on the compressor blades. This paper will be oriented towards the propagation of total pressure and total temperature non-uniformities in axial flow fans and compressors and their subsequent effect on downstream and upstream stages. An analytical technique will be used to correlate the inlet distortion patterns to the reduction of the stall/surge margin. A first part of this paper is dealing with the role of the inlet on the total pressure and temperature distortion at the fan or compressor face. A second part is concentrated on distortion propagation through the compressor. Given a total pressure or total temperature distortion entering a compressor, the methodology developed in this paper allows to predict the downstream total pressure and pressure ratio and therefore to give insight into the potential danger of a given inlet distortion pattern.